Blading

Patent metadata

Field	Value
Publication number	US-9316103-B2
Application number	US-201213683647-A
Country	US
Kind code	B2
Filing date	Nov 21, 2012
Priority date	Nov 25, 2011
Publication date	Apr 19, 2016
Grant date	Apr 19, 2016

Abstract

A blading for a turbomachine, particularly for a gas turbine, wherein thickened areas and depressions formed and disposed on a lateral wall having a plurality of blades such that at least one depression is disposed on a blade pressure side and at least one thickened area is disposed on a blade suction side for each blade of the plurality of blades.

First claim

What is claimed is:

1. A blading for a turbomachine in which a lateral wall has a plurality of blades, the blading comprising:
at least one depression disposed on a blade pressure side and at least one first thickened area disposed on a blade suction side for each blade of the plurality of blades; and
a pair of adjacent blades selected from the blades;
a second thickened area extending from the respective blade suction side of a first one of the pair of blades to the respective blade pressure side on a second one of the pair of blades, the second thickened area being in a half of the blading adjacent to an outlet side;
wherein the second thickened area is defined by a plurality of isolines that measure a height of the lateral wall at a plurality of points on the lateral wall in a direction orthogonal to the lateral wall;
wherein each isoline of the second thickened area has a first end and a second end; the first end terminating at the respective suction side of the first one of the blades, and the second end terminating at the respective pressure side of the second one of the blades.

2. The blading according to claim 1 , wherein the lateral wall is not contoured axially in front of and/or behind the first thickened areas and/or the at least one depression.

3. The blading according claim 1 , wherein the at least one depression and/or the at least one first thickened area extends in an axial direction over at least 10% of an axial grid length, but no more than 100% of the axial grid length.

4. The blading according claim 3 , wherein the depression and/or first thickened area extends in the axial direction over at least 30% of the axial grid length, but not more than 100% of the axial grid length.

5. The blading according to claim 1 wherein the at least one first thickened area disposed on the blade suction side and/or the at least one depression disposed on the blade pressure side is disposed in a half of the blade grid facing an inlet side.

6. The blading according to claim 1 , wherein the second thickened area is peripherally symmetrical or peripherally asymmetrical.

7. The blading according claim 1 wherein each blade has a rounded root surface in a region of a transition from the respective blade to the lateral wall.

8. The blading according to claim 1 wherein each blade has a bent transition in a region of a transition from the respective blade to the lateral wall.

9. The blading according to claim 8 wherein the bent transition is orthogonal.

10. A manufacturing method for a blading of a turbomachine having at least one reshaping and/or at least one cutting treatment such that thickened areas and depressions are formed in a lateral wall having a plurality of blades, each blade having a respective pressure side and a respective suction side, comprising the steps of forming at least one depression selected from the depressions on the respective blade pressure side and forming at least one thickened area selected from the thickened areas on the respective blade suction side for each blade of the plurality of blades; and
forming a second thickened area between a pair of adjacent blades selected from the plurality of blades so that the second thickened area extends from the respective blade suction side on a first one of the pair of blades to the respective blade pressure side on a second one of the pair of blades, the second thickened area being in a half of the blading adjacent to an outlet side;
wherein the second thickened area is defined by a plurality of isolines that measure a height of the lateral wall at a plurality of points on the lateral wall in a direction orthogonal to the lateral wall;
wherein each isoline of the second thickened area has a first end and a second end; the first end terminating at the respective suction side of the first one of the blades, and the second end terminating at the respective pressure side of the second one of the blades.

Assignees

• Mtu Aero Engines Gmbh

Inventors

• Passrucker Harald
• Wunderer Roland

Classifications

• F04D29/544

  Blade shapes · CPC title

• F01D5/143

  Contour of the outer or inner working fluid flow path wall, i.e. shroud or hub contour · CPC title

• Y02T50/673

  Cross-Sectional Technologies · mapped topic

• F01D5/145 Primary

  Means for influencing boundary layers or secondary circulations (for compressors F04D29/68) · CPC title

• Y10T29/49336

  Blade making · CPC title